254 results about "Airborne system" patented technology

An onboard system for determining the instantaneous weight and balance of an aircraft simply, reliably, accurately, and requiring a minimum amount of calibration includes a memory for storing previously determined breakout friction data of the aircraft's landing gear shock struts, sensors for sensing the pressures in the struts, the vertical loads exerted by the landing gear on the aircraft, and the attitude of the aircraft relative to the horizontal during loading or unloading thereof, and a computer for computing the vertical load in each of the landing gears from the stored calibration breakout friction data and the shock strut pressures, landing gear vertical loads and aircraft attitude sensed during the loading or unloading. The computer then computes the gross weight of the aircraft and the location of its center of gravity (CG) using the computed vertical loads in the landing gears.

The invention provides a general aviation flight monitoring airborne system based on an ADS-B (Automatic Dependent Surveillance-Broadcast). The system comprises an airborne ADS-B transceiver based on UAT (Ultra Aperture Terminal)\1090ES (Echo Sounding), a message processor based on the ADS-B and an airborne CDTI (Cockpit Display of Traffic Information) based on the ADS-B. The system provided by the invention has an ADS-B OUT / IN function and can be used for coding information input by an airborne FMS (flight management system), a GNSS (Global Navigation Satellite System), a barometric altimeter and a pilot, generating a message and broadcasting the message; and the system can receive flight status ADS-B messages of other airplanes and ground monitoring messages and separate UAT signals from 1090ES signals by virtue of a UAT data chain and a 1090ES data chain. The system provided by the invention can be used for respectively verifying, storing and parsing the flight status of the other airplanes\ground monitoring messages, messages of a local airplane, heartbeat messages of a host, graphical display navigation information, traffic information of the local airplane and traffic information of the other airplanes within a certain range of the local airplane.

The invention provides a flight control system, which comprises an airborne system and a ground system, wherein the airborne system comprises a miniature video camera, a GPS receiver, a GPS signal collection unit, a power supply monitoring unit, an overlapping unit and a microwave emitting unit, the miniature video camera and the GPS receiver are arranged outside an unmanned plane, the GPS signal collection unit, the power supply monitoring unit, the overlapping unit and the microwave emitting unit are arranged inside the unmanned plane, and the ground system comprises a microwave receiving unit, a video display and a remote control, wherein the miniature video camera is used for monitoring video images right ahead the unmanned plane in real time, the GPS signal collection unit is used for collecting and processing data transmitted from the GPS receiver to obtain flight parameters, the power supply monitoring unit is used for detecting and obtaining the power supply information of the unmanned plane, the overlapping unit is used for overlapping the flight parameters and / or the power supply information onto the video images, and the microwave emitting unit is used for emitting the overlapping results to the ground system. The invention can perfectly control the unmanned plane.

The invention discloses a communication navigation monitoring system based on a multi-mode data link. The communication navigation monitoring system based on the multi-mode data link comprises an airborne system, a Beidou commanding terminal, an ADS-B (automatic dependent surveillance-broadcast) ground station, a ground MC (mobile communication) base station and a ground data processing center, wherein a GNSS (global navigation satellite system) module is used for collecting positioning information in the airborne system, and data interaction is carried out between the GNSS module and a ground Beidou sending and receiving terminal via a satellite link; an airborne ADS-B module is used for sending and receiving ADS-B information; an MC data link is established by an airborne MC module; an airborne data processing module is used for carrying out link judgment and switching; in the ground data processing center, a data link management and control module is in charge of link selection; the link information is firstly pre-processed by a receiving data pre-processing module and is then processed by a data fusion module to be stored into a target state database module. According to the communication navigation monitoring system based on the multi-mode data link, which is disclosed by the invention, the modular design is adopted, the communication navigation monitoring system has the expandability, data link judgment and switching can be carried out in real time, and therefore operation cost is reduced.

A dumachine control system of coaxial pilotless heligyro comprises two sets of ground units and one set of heligyro unit. It is featured as forming said ground unit by control machine platform, flying control table , remote control coder, remote detection decoder, ground control computer, control emitter / receiver and control antenna; forming heligyro unit by control antenna, control emitter / receiver, control video processing combination and low speed signal regulator.

The invention relates to a low-attitude tracking system of unmanned aircraft on ground movable target and relative method. Wherein, said system comprises carrier system and ground system; the carrier system is formed by camera, table, carrier image sender and carrier data transmitter; the ground system is formed by image receiver, image collector, PC, and ground data transmitter; the tracking method comprises that extracting target via threshold value division, calculating out the position of target gravity center to find its position in track field, and manually interfering the track state. It uses several threshold values, which can be replaced to improve the track stability. The invention has high real-time property and stability.

The present invention is the flying control system and method for semi-autonomous flying of unattended aeroboat. The control system includes aeroboat borne system and ground system, the aeroboat borne system has structure comprising sensors, A / D converter, monolithic computer, analog multiplexer, executor, aeroboat borne data transmission module, remote controlled signal receiver, etc. connected together; and the ground system has PC, ground data transmission module and remote signal emitter. The aeroboat borne data transmission module and the remote controlled signal receiver in the aeroboat borne system associate with the ground data transmission module and the remote signal emitter of the ground system via RF signal. The control system can identify the mode channel signal and realize the mode switching among remote control, local remote control and autonomous flying.

The invention provides a pavement crack detection method, device and equipment of an aerial photography image. The method comprises that a deep high-dimension feature of a pavement area is extracted from the pavement aerial photography image, and a high-dimension feature graph is obtained according to the deep high-dimension feature; on the basis of the deep high-dimension feature of the pavementarea, positive and negative samples of the high-dimension feature graph are screened to distinguish pavement crack targets from a pavement background; and the pavement crack targets are classified andpositioned according to coordinates to obtain classification information and coordinate information of the pavement crack targets. The method, device and equipment can be applied to pavement crack detection of the aerial photography image with high-altitude motion or complex scene, and compared with routine crack detection algorithms, the method is more suitable for image collection of an unmanned airborne system, and the crack detection robustness of the aerial photography image is higher.

The invention discloses a wireless audio and video transmission system for transmission line helicopter routing inspection. The system comprises a helicopter airborne system, a ground station system and a command center end system, wherein the helicopter airborne system is connected with the ground station system in a wireless communication way; the ground station system is connected with the command center end system in an industrial Ethernet way; the helicopter airborne system further comprises a front end video acquisition and storage system, a video transmission system and a voice intercom system; the ground station system further comprises an audio and video receiving system, a local video monitoring system, a VOIP telephone system and an optical fiber transmission system; and the command center end system further comprises a video playing system, a picture recording system and a VOIP telephone system. Due to the adoption of the technical scheme, the system not only can change and improve the conventional line walking mode and work efficiency, but also can achieve real-time multi-channel video transmission, storage and voice intercom.

In high-efficiency power source applications, AC power is converted to DC power, which is isolated from the source and regulated. A level of performance is achieved that exceeds the power quality requirements of MIL-STD-704 over the extended frequency range, typically from about 360 Hz to 800 Hz. While high-efficiency and low-weight of the invention, among other benefits, are advantageous primarily in airborne systems, its use can be extended to terrestrial applications as well. The isolation, regulation and the main power processing are achieved by low-weight, high-frequency conversion stages arranged in 2 channels that produce the line harmonic content typical of the 12-pulse rectification. Control of the conversion stages provides effective rejection of line transients, while output ripple voltage is typically an order of magnitude lower than in conventional transformer rectifier units.

The invention provides an unmanned aerial vehicle (UAV) ground comprehensive detection system and a UAV ground comprehensive detection method, belonging to the field of UAV data processing. The UAV ground comprehensive detection system comprises a main program module, an electromechanical system detection module, a system parameter binding module, a system failure download and record module, a communication interface module, a power device detection module and a vehicle management system detection module, wherein all the modules, except the main program module, are independent of one another, and are respectively connected with the main program module; the UAV ground comprehensive detection system is also provided with data buses which are respectively connected with corresponding data bus interfaces of a UAV, so that data exchange is realized, and the UAV is detected. After the UAV ground comprehensive detection system and the UAV ground comprehensive detection method are used for detecting an aircraft, multiple detection devices prepared by preflight maintenance in the prior art can be replaced, so that maintenance devices are reduced, the maintenance cost is lowered, the complicated operation of the multiple devices is avoided, the preflight preparation time of the aircraft is effectively shortened, and the information interaction with a complicated airborne system is realized.

Onboard systems and methods for early detection that an aircraft is approaching a volcanic (ash) plume or a gas plume having a concentration of a volcanic gas which would be toxic to humans. The detection method generally comprises the steps of measuring the concentration of one or more volcanic gases in air circulating in a space inside an aircraft and generating an alarm when one or more measured volcanic gas concentrations exceed a respective user-specified threshold or when a pattern of volcanic gas concentration is recognized with a user-specified confidence level. These systems are configured so that the alarm indicates the proximity of dangerous levels of either a volcanic gas or of volcanic ash. In particular, the detection system utilizes the air circulating through an aircraft cabin or cockpit to enable use of low-cost, carry-on electronic devices.

The invention provides an agricultural plant protection unmanned aerial vehicle (UAV) planting control system which is composed of a vehicle-borne subsystem and a ground station subsystem. The vehicle-borne subsystem comprises a vehicle-borne GPS antenna (1), a vehicle-borne relative height detector (2), a vehicle-borne obstacle detector (3), and a vehicle-borne data returning and receiving system (4). The ground station subsystem comprises a ground station geographic information system (5), a ground station flight task planning and flight control system (6), and a ground station instruction receiving and sending system (7). According to the system of the invention, work currently needing vehicle-borne flight control is transferred to the ground, the air control part is only responsible for stability augmentation and obstacle detection, and a lot of path computation and flight control operation are managed and controlled by the ground in a unified manner. Therefore, the weight of the vehicle-borne system is reduced greatly, the difficulty in UAV developing is reduced, and the operation requirements of a variety of UAVs are satisfied effectively.

An improved positioning and data integrated processing method and system can substantially solve the problems encountered in the system integration of personal handheld applications, air, ground and water vehicles, an integrated GPS / inertial measurement unit consists of optional enhanced by other means to obtain user position, velocity, attitude, and airframe acceleration and rotation information and to distribute these data to other onboard systems, such as flight management systems, flight control systems, automatic dependent surveillance systems in the case of aircraft applications , cockpit displays, enhanced ground proximity warning system, weather radar and satellite communications system.

The invention discloses an airborne Aircraft Communication Addressing and Reporting System (ACARS) and a malfunction diagnosis and health management method thereof. The airborne system comprises a communication unit, a communication management unit, comprehensive modularized avionic equipment and a control / display unit. The comprehensive modularized avionic equipment comprises a data acquisition module, a data processing module, a status monitoring module and a health evaluation and malfunction diagnosis module. The airborne system communicates with a ground control center to achieve real-time information transmission between a plane and the ground; and meanwhile, the airborne system is provided with the data acquisition module, the data processing module, the status monitoring module and the health evaluation and malfunction diagnosis module, the Aircraft Communication Addressing and Reporting System (ACARS) can be subjected to health condition monitoring and malfunction diagnosis, and therefore the safety and the reliability of the Aircraft Communication Addressing and Reporting System (ACARS) are further improved, and the flight safety is ensured.

In various representative aspects, an airborne delivery system according to various aspects of the present invention comprises a container and an autorotating rotor system. The container may contain contents, and the rotor system facilitates control of at least a portion of the flight of the airborne system and the descent. Exemplary features may include a guidance system, for example to guide and control the airborne system, and a wing for gliding.

The invention discloses an unmanned airborne system for SAR imaging and moving-target detection by utilizing millimeter-wave Ka-frequency-band frequency modulated continuous waves. Ka-frequency-band wavelength is shorter, and an antenna is smaller than a lower-frequency-band antenna in size under the condition of the same beam width. A millimeter-wave device is smaller than a lower-frequency-band device in size, weight and power consumption. The system can be miniaturized, images finer than other lower-frequency-band images can be obtained by utilizing millimeter-wave Ka-frequency-band signals to perform SAR imaging, target edge and corner characteristics are obvious, and target recognition is facilitated. Ka-frequency-band signals of higher relative band width can be obtained, so that higher image resolution can be obtained compared with lower-frequency-band signals. The system for SAR imaging by utilizing the frequency modulated continuous waves is simple in device, low in complexity, small in data volume by adopting a de-chirp mode and capable of performing real-time imaging processing.

Onboard systems and methods for detection of airborne volcanic ash. One or more cameras are added to an aircraft. Each camera is configured to view a volume of air illuminated by a standard aircraft light, such as a strobe warning light (e.g., located on a wing tip) or a forward-facing landing light (e.g., located in the nose). Each camera is connected to a data processor. When diffuse volcanic ash is present, it scatters light transmitted from the standard aircraft light. Each camera converts impinging backscattered light into digital data which is sent to the processor. The processor processes the data from the camera or cameras to derive a measurement of the backscattered light and issues an alert when the amount and type of backscatter are compatible with the presence of volcanic ash.

This invention is directed toward a computer-controlled auxiliary fuel tank system that works with both gas and diesel-fueled vehicles, and can operate independently, or in combination with an auxiliary fuel tank, auxiliary fuel pump, sending unit, check valves, inlet and outlet fuel lines, wiring harness, computer module, auxiliary emissions canister assembly, vehicle installation means, and LCD and LED display devices. The invention is not dependent upon any other computer systems and is fully transparent to any on-board systems. In addition to overseeing the transfer of fuel from the auxiliary tank to the OEM tank, the fuel monitoring system (FMS) monitors a variety of functions of the vehicle, and from that data can calculate and display a wide range of information for the user, and is fully user calibratable. The invention not only warns of low fuel situations, but also provides a wide range of diagnostic tools to analyze and display problems with the fuel system.

An airborne system for producing electricity from wind energy includes a shaft, wind turbines rotatably mounted to the shaft and arranged to rotate independently in opposite directions when subjected to the same wind, and generators arranged to convert rotation of the turbines into electricity. A lifting section includes combination of kites and lighter than air balloons, generating a lifting force that caused the system being airborne at desire altitude. The center of gravity of the system is lower than the center of lift of the system; when the turbines of the system exposed to wind and start to rotate, torques are inducing on the shaft of the system; these torques are balancing each other and the remaining deferential torque being balanced by returning torque that is generated by the angular deviation of the center of gravity from it's lowest position, the magnitude of this returning torque, increasing as the angular deviation increased, until the system reach angular stability; electricity is generating and conducted through tether to an anchoring section for usage.

The invention discloses an extreme-low-altitude laser radar digital terrain mapping system and an extreme-low-altitude laser radar digital terrain mapping method of a small-sized unmanned helicopter. The system is formed by an airborne system and a ground station system, wherein the airborne system is used for accurately collecting data of each sensor, carrying out synchronization processing on the data of the sensors and navigation control of the unmanned helicopter, and can realize data interaction with data of the ground station system through wireless receiving and dispatching equipment; the ground station system is used for receiving and processing data from an airborne laser radar hardware system or checking and processing a data file in an offline manner; the airborne system is formed by a coprocessor and a main processor; and the coprocessor is used for collecting gesture data and position data of the system or realizing the navigation control of the airborne system. According to the extreme-low-altitude laser radar digital terrain mapping system, a mode of matching the coprocessor with the main processor is utilized so that the requirements of the instantaneity and the stability of the navigation control of the small-sized unmanned helicopter are guaranteed, the system is flexible and the function of the airborne system is conveniently expanded; and the system has the advantages of low power consumption, low cost, high integration, high efficiency and the like.

An airborne system for producing electricity from wind energy includes a shaft, wind turbines rotatably mounted to the shaft and arranged to rotate independently in opposite directions when subjected to the same wind, and generators arranged to convert rotation of the turbines into electricity. A lifting section includes combination of kites and lighter than air balloons, generating a lifting force that caused the system being airborne at desire altitude. The center of gravity of the system is lower than the center of lift of the system; when the turbines of the system exposed to wind and start to rotate, torques are inducing on the shaft of the system these torques are balancing each other and the remaining deferential torque being balanced by returning torque that is generated by the angular deviation of the center of gravity from it's lowest position, the magnitude of this returning torque, increasing as the angular deviation increased, until the system reach angular stability; electricity is generating and conducted through tether to an anchoring section for usage.

An embodiment of an open data network system facilitates communication between applications related to operation of a vehicle, such as an aircraft, and re-use of components in different systems and implementations. A switch / router communicates data between on-board systems. A server communicates with the switch / router and provides at least one of processing services and storage services to the on-board systems via the switch / router. A network manager communicates with the switch / router to direct the switch / router in selectively allowing access between the on-board systems. In other embodiments, an avionics interface unit communicates with the switch / router and enable communications between at least one avionics system and at least one of the on-board systems. Other embodiments selectively enable on-board systems to communicate with a ground-based network to provide communications between the aircraft and a stakeholder in the operation of the aircraft while isolating flight-critical avionics and flight communications systems from the open data network.

Airborne system for producing electricity from wind includes at least one shaft, one or more wind turbines rotatably mounted to each shaft, and generators that convert rotation of the turbine(s) into electricity. A lifting section is connected to the shaft(s) and generates a lifting force that causes the system to be airborne. A center of gravity of the system is lower than its center of lift. When the turbines are exposed to wind and rotate (at least one in one direction and another in an opposite direction), torques induced on the shaft(s) of the system balance each other and remaining deferential torque is balanced by returning torque that is generated by the angular deviation of the center of gravity from its lowest position. A magnitude of this returning torque increases as the angular deviation increases until the system reach angular stability. Electricity is generated and conducted for storage or usage.

Onboard systems and methods for early detection that an aircraft has flown into a volcanic ash plume embedded within a water vapor cloud having a concentration of a volcanic ash which would be dangerous to an aircraft. The detection method generally comprises the steps of measuring the infrared emission characteristics of a jet engine exhaust and generating a detection signal when the intensity of infrared emissions at or near a spectral peak wavelength exceeds a threshold.

The invention provides an all-purpose aircraft airborne system and a communication supervision system based on the Tiantong-01 satellite. The communication supervision system comprises the all-purposeaircraft airborne system, a ground data processing system, and a satellite system. The satellite system is a Tiantong communication satellite, and serves as a communication circuit of the all-purposeaircraft airborne system and the ground data processing system. The ground data processing system tracks the flight position and track of an aircraft according to the positioning information transmitted by the all-purpose aircraft airborne system, and achieves the real-time voice and data communication. The communication supervision system can carry out the automatic switching of a transmission mode according to the intensity of different satellite signals, and achieve the selective call of one or more all-purpose aircrafts from the ground through the voice communication function of the Tiantong-01 satellite while achieving the voice communication between the ground and the all-purpose aircrafts. The system can achieve the seamless supervision and voice communication of the all-purpose aircrafts in an integrated manner, thereby greatly saving the construction and operation cost of the ground equipment.

The invention provides a ground control station based on an airborne system of an unmanned aerial vehicle. The ground control station comprises a remote control operation panel and a display screen panel, wherein the display screen panel comprises a flight state display screen, a flight path display screen, an online consultation display screen and a task system display screen; the display screen panel is further provided with function buttons of all the display screens; the remote control operation panel comprises an accelerator rocking bar, a cloud deck knob, a dialing knob, a computer system control region, a flight control rocking bar, a flight mode selection button and a remote control takeover button. The ground control station provided by the invention is provided with the four screens in total so that various states of the unmanned aerial vehicle can be independently displayed and an operator can conveniently know about a plurality of types of needed information; the remote control operation panel is reasonably arranged so that the operator can conveniently manipulate the unmanned aerial vehicle; the ground control station is used as supplementation and upgrading of a handheld portable ground station and provides a more comfortable operation mode and more flight functions and task functions; by using airborne advantages of the ground control station, measurement and control operation in a relatively far distance can be carried out.

This invention is directed toward a computer-controlled auxiliary fuel tank system that works with both gas and diesel-fueled vehicles, and can operate independently, or in combination with an auxiliary fuel tank, auxiliary fuel pump, sending unit, check valves, inlet and outlet fuel lines, wiring harness, computer module, auxiliary emissions canister assembly, vehicle installation means, and LCD and LED display devices. The invention is not dependent upon any other computer systems and is fully transparent to any on-board systems. In addition to overseeing the transfer of fuel from the auxiliary tank to the OEM tank, the fuel monitoring system (FMS) monitors a variety of functions of the vehicle, and from that data can calculate and display a wide range of information for the user, and is fully user calibratable. The invention not only warns of low fuel situations, but also provides a wide range of diagnostic tools to analyze and display problems with the fuel system.